Method and apparatus for detecting conditions conducive to ice formation

ABSTRACT

A method for detecting ambient conditions conducive to ice formation. The method includes the steps of measuring at least one parameter selected from a group of parameters consisting of a static pressure, a total pressure, a total temperature, a dew point temperature, and a liquid water content, and determining whether ambient conditions are conducive to ice formation based on the measured parameter.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. application Ser. No.11/626,282, filed on Jan. 23, 2007, which is a divisional of U.S.application Ser. No. 10/417,309, filed on Apr. 16, 2003, which isincorporated herein in its entirety.

BACKGROUND OF THE INVENTION

The present invention relates generally to ice formation, and morespecifically to a method and apparatus for detecting conditionsconducive to ice formation.

During flight and while on the ground, aircraft may encounteratmospheric conditions that cause ice to form on critical flightsurfaces, such as wings, stabilizers, rudders, and ailerons, propulsionsystem components, such as engine inlets, propellers, and engine rotors,in addition to the fuselage of the aircraft. Accumulating ice, if notremoved, can add excessive weight to the aircraft and alter theaerodynamic and propulsive performance of the aircraft, possibly causingunsafe flying conditions. Even small amounts of ice on aerodynamicsurfaces, such as wings, the tail, propellers, and the like, cansignificantly alter flight characteristics. In summary, accumulating icemay cause unsafe flying conditions.

Some known ice detection systems utilize an ice detection system tonotify the flight crew of the formation of a threshold thickness of iceon a detection system sensor. In such known systems, the formation ofice on the sensor is essential for a warning signal. Therefore, suchknown systems respond slowly to ambient air conditions and thus warn theflight crew and/or activate ice protection systems after ice has alreadyaccumulated on surfaces of the aircraft. Additionally, such known icedetection systems may have limited utility due to differences in ambientconditions near the critical flight surfaces and the sensor. Extensiveand costly flight-testing may thus be required to validate sensorlocation on the airframe.

SUMMARY OF THE INVENTION

In one aspect, a method is provided for detecting ambient conditionsconducive to ice formation. The method includes the steps of measuringat least one parameter selected from a group of parameters consisting ofa static pressure, a total pressure, a total temperature, a dew pointtemperature, and a liquid water content, and determining whether ambientconditions are conducive to ice formation based on the measuredparameter.

In another aspect, a system is provided for detecting ambient conditionsconducive to ice formation. The system includes a processor, a firstsensor operatively connected to the processor and configured to measureat least one of a static pressure and a total pressure, a second sensoroperatively connected to the processor and configured to measure a totaltemperature, and a third sensor operatively connected to the processorand configured to measure a dew point temperature. The processor isconfigured to determine whether ambient conditions are conducive to iceformation based on at least one parameter selected from a group ofparameters consisting of the measured static pressure, the measuredtotal pressure, the measured total temperature, and the measured dewpoint temperature.

In yet another aspect, an aircraft includes an airframe, a processormounted on the airframe, a first sensor operatively connected to theprocessor and configured to measure at least one of a static pressureand a total pressure, a second sensor operatively connected to theprocessor and configured to measure a total temperature, and a thirdsensor operatively connected to the processor and configured to measureat least one of a dew point temperature and a liquid water content. Theprocessor is configured to determine when ambient air conditions areconducive to ice formation on an external surface of the aircraft basedon at least one parameter selected from a group of parameters consistingof the measured air static pressure, the measured air total pressure,the measured air total temperature, the measured air dew pointtemperature, and the measured air liquid water content.

In even another aspect, a system is provided for detecting ambientconditions conducive to ice formation. The system includes a processor,a first sensor operatively connected to the processor and configured tomeasure at least one of a static pressure and a total pressure, a secondsensor operatively connected to the processor and configured to measurea total temperature, and a third sensor operatively connected to theprocessor and configured to measure a liquid water content. Theprocessor is configured to determine whether ambient conditions areconducive to ice formation based on at least one parameter selected froma group of parameters consisting of the measured static pressure, themeasured total pressure, the measured total temperature, and themeasured liquid water content.

Other features of the present invention will be in part apparent and inpart pointed out hereinafter.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective of an aircraft including an exemplary icingconditions detection system;

FIG. 2 is a schematic of the icing conditions detection system shown inFIG. 1 and an ice protection system for use with the aircraft shown inFIG. 1;

FIG. 3 is a schematic of a sensor system for use with the detectionsystem shown in FIGS. 1 and 2;

FIG. 4 is a schematic of an alternative sensor system for use with thedetection system shown in FIGS. 1 and 2;

FIG. 5 is a schematic of another alternative sensor system for use withthe detection system shown in FIGS. 1 and 2;

FIG. 6 is a flow chart illustrating an exemplary method of detectingconditions conducive to ice formation using the icing conditionsdetection system shown in FIGS. 1 and 2 including a dew pointtemperature sensor;

FIG. 7 is a graph illustrating the Federal Aviation Regulations Part 25Appendix C atmospheric icing conditions in terms of temperature versusambient static pressure; and

FIG. 8 is a flow chart illustrating an exemplary method of detectingconditions conducive to ice formation using the icing conditionsdetection system shown in FIGS. 1 and 2 including a liquid water contentsensor.

Corresponding reference characters indicate corresponding partsthroughout the several views of the drawings.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

Referring now to the drawings, and more specifically to FIGS. 1 and 2,an aircraft is designated in its entirety by the reference numeral 20.The aircraft 20 includes an airframe 22, an icing conditions detectionsystem (ICDS), generally designated by the reference numeral 24, and anice protection system controller 26. The airframe 22 includes a fuselagesection 28 and a pair of wings 30 extending outwardly from the fuselage28. Both the fuselage 28 and the wings 30 are covered in a skin formingan outer surface 32 of the aircraft 20. Each wing 30 includes a leadingedge 34. The ice protection system controller 26 is operativelyconnected to an ice protection system (not shown) to control operationof the ice protection system. The ice protection system is operativelyconnected to the critical sections of the aircraft outer surface 32, forexample, wing leading edges 34 and engine inlet surfaces (not shown), toeliminate ice from the surface 32 in any suitable manner. It should beunderstood that as described herein the ice protection system may be anysuitable system operative to eliminate ice in any suitable manner, suchas, for example, a pneumatic thermal system, an electrical thermalsystem, a pneumatic boot mechanical system, and/or an electro-impulsemechanical system. The above examples of ice protection systems areexemplary only and are not intended to limit the type of ice protectionsystem referred to herein. Additionally, it should be understood that asused herein the aircraft outer surface 32 is intended to include anysurface of the aircraft 20 exposed to ambient conditions and/orsusceptible to the formation of ice thereon.

Although the ice protection system controller 26 is illustrated anddescribed herein in the exemplary manner, it should be understood thatthe ice protection system controller 26 may be mounted on the airframe22 anywhere and in any suitable manner, with respect to the airframe 22and the outer surface 32, facilitating operating the ice protectionsystem to eliminate ice from any portion of the outer surface 32.

The ICDS 24 includes a processor 36 mounted on the airframe 22 andoperatively connected to the ice protection system controller 26, and aplurality of sensor modules 38, 40, 42 mounted on the airframe 22 andoperatively connected to the processor 36. More specifically, in theexemplary embodiments, each sensor module 38, 40, 42 is mounted on theairframe structures (not shown) such that each module 38, 40, 42provides measurement of a predetermined parameter or parameters within apredetermined accuracy. Although the sensor modules 38, 40, 42 areillustrated and described herein in the exemplary manner, it should beunderstood that the airframe 22 may include any number of sensor modulesoperatively configured to measure any desired parameter, and it shouldalso be understood that such sensor modules may be mounted on theairframe 22 anywhere and in any suitable manner, with respect to theairframe 22 and the outer surface 32, facilitating measurement of theselected parameter within a predetermined accuracy. For example, in oneembodiment (not shown), one or more of the sensors 38, 40, 42 aremounted on the airframe such that the sensor(s) protrudes in thefree-stream.

In an exemplary embodiment, the sensor 38 is a conventional pressuresensor 38 configured to measure a static pressure (PS) and a totalpressure (PT), the sensor 40 is a conventional temperature sensor 40configured to measure a total temperature (TT), and the sensor 42 is aconventional dew point sensor 42 configured to measure a dew pointtemperature (TD). In one embodiment, the conventional pressure sensor 38is a pitot-static pressure sensor. The dew point sensor 42 may be anysuitable sensor type, for example, optical, acoustic, or capacitive. Inone embodiment, the dew point sensor 42 is a hygrometer. In anotherembodiment, the dew point sensor 42 is a DewPro® MMY 35 dew pointtransmitter, commercially available from General Eastern InstrumentsCorporation of Woburn, Mass. In an alternative exemplary embodiment, thesensor 42 is a liquid water content sensor 42 configured to measureambient air liquid water content (LWC). The liquid water content sensor42 may be any suitable sensor type, for example, optical, acoustic, orcapacitive. In an alternative embodiment, the detection system 24includes separate sensor modules (not shown) for measuring staticpressure PS and total pressure PT. Further, in yet another alternativeembodiment (not shown), the detection system 24 includes both a dewpoint temperature sensor and a liquid water content sensor. Any of thesensor modules 38, 40, 42 may be designated herein as a first, a second,a third, and/or a fourth sensor. The pressure sensor 38 and temperaturesensor 40 are well known in the art and therefore will not be discussedin more detail herein.

In an alternative embodiment (not shown), the detection system 24 mayinclude other sensor types configured to measure ambient air moistureconditions (either by direct measurement or by explicit or empiricalcomputational methods using the ambient static pressure PS, totalpressure PT, and/or total temperature TT) in addition to, or inalternative to, a dew point temperature sensor and/or a liquid watercontent sensor, such as, for example, a sensor module configured tomeasure water vapor pressure in ambient air, a sensor module configuredto measure relative humidity, and/or a sensor module configured tomeasure specific moisture content. These other sensor types configuredto measure ambient air moisture conditions are conventional and wellknown to those experienced in the science of psychometrics, andtherefore will not be discussed in more detail herein. Any of theseother sensor modules configured to measure ambient air moistureconditions may be designated herein as a first, a second, a third,and/or a fourth sensor.

FIG. 3 is a schematic of a sensor system 80 for use with the icingconditions detection system 24 (FIGS. 1 and 2). More specifically, FIG.3 illustrates one embodiment of a sensor system 80 for measuring ambientmoisture conditions, such as, for example, dew point temperature, liquidwater content, vapor pressure, relative humidity, and/or specificmoisture content. The system 80 is mounted on the airframe 22 (FIG. 1)and includes the sensor 42, a filter 82, a sampling pump 84, and aheated inlet 86 in fluid communication with ambient air adjacent theaircraft 20 (FIG. 1). In one embodiment, the filter 82 is a centrifugetype filter. The sampling pump 84 is operatively connected to theprocessor 36 (FIGS. 1 and 2) and receives an input 88 from a ground/airswitch 90. It should be understood that the ground/air switch may bereplaced with any suitable device configured to indicate whether theaircraft 20 is on the ground or in flight. When the aircraft 20 is onthe ground, the switch 90 facilitates operation of the sampling pump 84such that the pump 84 draws ambient air through the heated inlet 86. Theair drawn through the heated inlet 86 travels through the filter 82 tothe sensor 42. The heated inlet 86 vaporizes liquid water present in theair drawn therethrough. The filter 82 removes contaminants from the airsuch that clean air is delivered to the sensor 42. The sensor 42 outputs92 the measured moisture condition parameter of the ambient air to theprocessor 36. When the aircraft 20 is on the ground, the ambient airdischarges from the sensor 42 and flows through a check valve 98, thepump 84, and discharges through an outlet 94. When the aircraft 20 is inflight, the switch 90 suspends operation of the sampling pump 84, thesensor 42 receives ambient air from the heated inlet 86 as a result ofram air pressure, and the ambient air discharges from the sensor 42,flows through a check valve 96, and discharges through the outlet 94. Inone embodiment, the ambient air flows through the sensor 42 at a ratebetween about 0.25 standard cubic feet per hour and about 5.5 standardcubic feet per hour. Additionally, in one embodiment, the system 80includes a suitable flow control device (not shown) such as a pressureregulator to control the flow rate of air through the sensor 42.

FIG. 4 is a schematic of an alternative sensor system 120 for use withthe icing conditions detection system 24 (FIGS. 1 and 2). Morespecifically, FIG. 4 illustrates an alternative embodiment of a sensorsystem 120 for measuring ambient moisture conditions, such as, forexample, dew point temperature, liquid water content, vapor pressure,relative humidity, and/or specific moisture content. The system 120 ismounted on the airframe 22 (FIG. 1) and includes the sensor 42, a heatedinlet 122, and an outlet 124. The heated inlet 122 is in fluidcommunication with a duct 126 contained in the aircraft 20 (FIG. 1). Forexample, the duct 126 may be a core engine bypass (fan air) or an enginebleed air duct. The aircraft 20 includes an engine (not shown) mountedon the airframe 22. The engine includes a fan (not shown). At least aportion of the air passing through the fan travels through the duct 126.In one embodiment, the system 120 includes a filter (not shown) forremoving contaminants from the fan air so clean air is delivered to thesensor 42. The sensor 42 receives the fan air from the heated inlet 122and outputs 130 the measured moisture condition parameter of the air tothe processor 36 (FIGS. 1 and 2). The heated inlet 122 vaporizes liquidwater present in the air. The air received by the sensor 42 dischargesthrough the outlet 124.

FIG. 5 is a schematic of another alternative sensor system 150 for usewith the icing conditions detection system 24 (FIGS. 1 and 2). Morespecifically, FIG. 5 illustrates another alternative embodiment of asensor system 150 for measuring ambient moisture conditions, such as,for example, dew point temperature, liquid water content, vaporpressure, relative humidity, and/or specific moisture content. Thesystem 150 is mounted on the airframe 22 (FIG. 1) and includes thesensor 42, a heated inlet 152, and an outlet 154. The aircraft 20(FIG. 1) includes an air-conditioning system 164 mounted on the airframe22 for providing air-conditioned air for passenger, crew, and equipmentconditioning of the aircraft 20. The heated inlet 152 is in fluidcommunication with an air-conditioning system ram air duct 156 containedwithin the air-conditioning system 164 and carries a flow of ambientair. The heated inlet 152 is in fluid communication with the duct 156upstream from a condensed moisture spray nozzle system 158, a pluralityof heat exchangers 160, and a fan 162, each positioned within the duct156 as illustrated in FIG. 5. The outlet 154 is in fluid communicationwith the duct 156 downstream from the nozzle system 158 and the heatexchangers 160, and upstream from the fan 162. In one embodiment, thesystem 150 includes a filter (not shown) for removing contaminants fromthe air such that clean air is provided to the sensor 42. The sensor 42receives air from the duct 156 through the heated inlet 152, and outputs166 the measured moisture condition parameter of the air to theprocessor 36 (FIGS. 1 and 2). The air discharges through the outlet 154back into the duct 156. In one embodiment, the fan 162 is one of anelectrical, a pneumatic, and an air-cycle fan.

FIG. 6 is a flow chart illustrating an exemplary method of detectingconditions conducive to ice formation on the aircraft surface 32(FIG. 1) using the icing conditions detection system 24 (FIGS. 1 and 2),wherein ambient air moisture conditions are determined using a dew pointtemperature sensor 42 (FIGS. 1 and 2). The method includes measuring thestatic pressure PS of ambient air adjacent the aircraft 20 using thepressure sensor 38, measuring the total pressure PT of the ambient airadjacent the aircraft 20 using the pressure sensor 38, measuring thetotal temperature TT of the ambient air adjacent the aircraft 20 usingthe temperature sensor 40, and measuring the dew point temperature TD ofthe ambient air adjacent the aircraft 20 using the dew point temperaturesensor 42. The PS, PT, TT, and TD measurements are input into theprocessor 36 (FIGS. 1 and 2) from the respective sensors 38, 40, 42. Theprocessor 36 determines the static temperature (TS) of the ambient airadjacent the aircraft 20. In one embodiment, the processor 36 calculatesthe static temperature TS using the measured static pressure PS, themeasured total pressure PT, and the measured total temperature TT.Furthermore, in one embodiment, the processor 36 calculates the statictemperature TS using the following relationships between the measuredstatic pressure PS, the measured total pressure PT, and the measuredtotal temperature TT:

$\begin{matrix}{{\frac{PT}{PS} = \left\lbrack {1 + {\frac{\gamma - 1}{2}M^{2}}} \right\rbrack^{\frac{\gamma}{\gamma - 1}}};} & (1)\end{matrix}$

wherein γ=ratio of specific heats at constant pressure and constantvolume;

for air, γ=1.4;

$\begin{matrix}{{\frac{PT}{PS} = \left\lbrack {1 + {0.2M^{2}}} \right\rbrack^{3.5}};} & (2) \\{{\left( \frac{PT}{PS} \right)^{\frac{1}{3.5}} = {1 + {0.2M^{2}}}};} & (3) \\{{\frac{TT}{TS} = {1 + {\frac{\gamma - 1}{2}M^{2}}}};} & (4)\end{matrix}$

wherein TT and TS are in degrees Rankine;

for air, γ=1.4;

$\begin{matrix}{{\frac{TT}{TS} = {1 + {0.2M^{2}}}};} & (5) \\{{{\frac{TT}{TS} = \left( \frac{PT}{PS} \right)^{0.2857}};}{and}} & (6) \\{{TS} = {\left( \frac{TT}{\left( \frac{PT}{PS} \right)^{0.2857}} \right).}} & (7)\end{matrix}$

The processor 36 uses the determined static temperature TS to determineif the ambient temperature conditions are conducive to ice formation.More specifically, the processor 36 compares the determined statictemperature TS with a minimum temperature for icing (T_(min)) and amaximum temperature for icing (T_(max)). As described below, if theprocessor 36 determines the determined static temperature TS is outsidethe defined temperature limits of T_(min) and T_(max), the processor 36concludes the ambient air static temperature TS is not conducive to iceformation and determines if the ice protection system, if operating,should be de-activated. FAR Part 25 Appendix C indicates that incontinuous maximum (stratiform clouds) atmospheric icing conditions,icing can occur at temperatures up to 32° F. from sea level to 12,000feet (9.35 psia) and at decreasing temperatures from 32° F. to −4° F.for altitudes from 12,000 feet (9.35 psia) to 22,000 feet (6.21 psia).FAR Part 25 Appendix C also indicates that in the intermittent maximum(cumuliform clouds) atmospheric icing conditions, icing can occur attemperatures up to 26° F. for altitudes from sea level to 12,000 feet(9.35 psia) and at decreasing temperatures from 26° F. to −40° F. foraltitudes from 12,000 feet (9.35 psia) to 29,000 feet (4.57 psia). FIG.7 is a graph illustrating the FAR Part 25 Appendix C icing temperatureand pressure boundaries for both continuous maximum and intermittentmaximum atmospheric icing conditions in terms of temperature versusambient static pressure PS. FIG. 7 also illustrates the ambient statictemperature TS (envelope ABCD) used by the processor 36.

In the exemplary embodiments, the T_(min) and T_(max) are pre-selectedas constants, wherein T_(min) is selected as −40° F. and T_(max) isselected as +50° F. It should be understood that constant values for theT_(min) and T_(max) other than those exemplified herein may be used. Inan alternative embodiment, the T_(min) and T_(max) are defined as afunction of ambient static pressure PS. In one alternative embodiment,the processor 36 determines the T_(min) and the T_(max) for the measuredstatic pressure PS using a table, similar to FIG. 7, stored in theprocessor 36, or alternatively a memory (not shown) operativelyconnected to the processor 36, and plots the T_(min) and T_(max) versusambient static pressure PS. In another alternative embodiment, theprocessor 36 determines the T_(min) and T_(max) for the measured staticpressure PS using a mathematical relationship stored in the processor36, or alternatively a memory (not shown) operatively connected to theprocessor 36, that calculates the T_(min) and T_(max) as a function ofambient static pressure PS.

As discussed above, the processor 36 compares the determined statictemperature TS with the T_(min). If the processor determines thedetermined static temperature TS is less than the T_(min), the processor36 concludes the ambient air static temperature, and more specificallythe determined static temperature TS, is not conducive to ice formation,and determines if the ice protection system (not shown), if operating,should be de-activated. In one embodiment, when the processor 36concludes the ambient air static temperature is not conducive to iceformation, the processor 36 sends an advisory signal to notify theaircraft flight crew the ambient air temperature is not conducive to iceformation. To determine if the ice protection system should bedeactivated, the processor 36 compares the determined static temperatureTS to the difference between the T_(min) and a dead-band minimumtemperature value (δT_(min)). The δT_(min) provides increased safety andprevents cyclic activation and de-activation of the ice protectionsystem when the ambient air temperature, and more specifically thedetermined static temperature TS, is marginally conducive to iceformation. If the processor 36 determines that the determined statictemperature TS is less than the difference between the T_(min) and theδT_(min), the processor 36 sends an output signal to the ice protectionsystem controller 26 to de-activate the ice protection system if it isoperating, and the processor re-starts the method beginning withmeasuring the static pressure PS, the total pressure PT, the totaltemperature TT, and the dew point temperature TD of the ambient air. Inone embodiment, when the ice protection system has been de-activated,the processor 36 sends an advisory signal to notify the aircraft flightcrew the ice protection system has been de-activated.

If the processor 36 determines the determined static temperature TS isgreater than or equal to the difference between the T_(min) and theδT_(min), the processor 36 maintains the operating status of the iceprotection system and re-starts the method beginning with measuring thestatic pressure PS, the total pressure PT, the total temperature TT, andthe dew point temperature TD of the ambient air. In one embodiment, whenthe processor 36 maintains the operating status of the ice protectionsystem, the processor 36 sends an advisory signal to notify the aircraftflight crew that the operating status of the ice protection system isbeing maintained.

If the processor 36 determines the determined static temperature TS isgreater than or equal to the T_(min), the processor 36 concludes theambient air static temperature, and more specifically the determinedstatic temperature TS, is conducive to ice formation. In one embodiment,when the processor 36 concludes the ambient air temperature is conduciveto ice formation, the processor 36 sends an advisory signal to notifythe aircraft flight crew that the ambient air temperature is conduciveto ice formation.

As discussed above, the processor 36 then compares the determined statictemperature TS with the T_(max). If the processor determines thedetermined static temperature TS is greater than or equal to theT_(max), the processor 36 concludes the ambient air static temperature,and more specifically the determined static temperature TS, is notconducive to ice formation, and determines if the ice protection system,if operating, should be de-activated. In one embodiment, when theprocessor 36 concludes the ambient air static temperature is notconducive to ice formation, the processor 36 sends an advisory signal tonotify the aircraft flight crew the ambient air temperature is notconducive to ice formation. To determine if the ice protection systemshould be deactivated, the processor 36 compares the determined statictemperature TS to the combination of the T_(max) and a dead-band maximumtemperature value (δT_(max)). The δT_(max) provides increased safety andprevents cyclic activation and de-activation of the ice protectionsystem when the ambient air temperature, and more specifically thedetermined static temperature TS, is marginally conducive to iceformation. If the processor 36 determines that the determined statictemperature TS is greater than or equal to the combination of theT_(max) and the δT_(max), the processor 36 sends an output signal to theice protection system controller 26 to de-activate the ice protectionsystem if it is operating, and the processor re-starts the methodbeginning with measuring the static pressure PS, the total pressure PT,the total temperature TT, and the dew point temperature TD of theambient air. In one embodiment, when the ice protection system has beende-activated, the processor 36 sends an advisory signal to notify theaircraft flight crew the ice protection system has been de-activated.

If the processor 36 determines the determined static temperature TS isless than the combination of the T_(max) and the δT_(max), the processor36 maintains the operating status of the ice protection system andre-starts the method beginning with measuring the static pressure PS,the total pressure PT, the total temperature TT, and the dew pointtemperature TD of the ambient air. In one embodiment, when the processor36 maintains the operating status of the ice protection system, theprocessor 36 sends an advisory signal to notify the aircraft flight crewthat the operating status of the ice protection system is beingmaintained.

If the processor 36 determines the determined static temperature TS isless than the T_(max), the processor 36 concludes the ambient air statictemperature, and more specifically the determined static temperature TS,is conducive to ice formation. In one embodiment, when the processor 36concludes the ambient air temperature is conducive to ice formation, theprocessor 36 sends an advisory signal to notify the aircraft flight crewthat the ambient air temperature is conducive to ice formation.

In the exemplary embodiments, the dead-band temperature values δT_(min)and δT_(max) are pre-selected as constants, wherein the δT_(min) isselected as 2° F. and the δT_(max) is selected as 5° F. It should beunderstood that constant values for the δT_(min) and the δT_(max) otherthan those exemplified herein may be used. In an alternative embodiment,the dead-band temperature values δT_(min) and δT_(max) are defined as afunction of ambient conditions, and more specifically ambient staticpressure PS.

The processor 36 then determines whether the ambient humidity conditionsare conducive to ice formation. More specifically, the processor 36compares the determined static temperature TS with the measured dewpoint temperature TD. If the processor 36 determines the determinedstatic temperature TS is greater than or equal to the measured dew pointtemperature TD, the processor 36 concludes the ambient air humidity isnot conducive to ice formation, and determines if the ice protectionsystem, if operating, should be de-activated. In one embodiment, whenthe processor 36 concludes the ambient air humidity is not conducive toice formation, the processor 36 sends an advisory signal to notify theaircraft flight crew that the ambient air humidity is not conducive toice formation. To determine if the ice protection system should bedeactivated, the processor 36 compares the determined static temperatureTS to the combination of the measured dew point temperature TD and adead-band dew point value (DTD). The dead-band dew point value DTDprovides additional safety and prevents cyclic activation andde-activation of the ice protection system when the ambient air humidityis marginally conducive to ice formation. If the processor 36 determinesthe determined static temperature TS is greater than or equal to thecombination of the measured dew point temperature TD and the dead-banddew point value DTD, the processor 36 sends an output signal to the iceprotection system controller 26 to de-activate the ice protection systemif it is operating, and the processor 36 re-starts the method beginningwith measuring the static pressure PS, the total pressure PT, the totaltemperature TT, and the dew point temperature TD of the ambient air. Inone embodiment, when the ice protection system has been de-activated,the processor 36 sends an advisory signal to notify the aircraft flightcrew the ice protection system has been de-activated.

In one embodiment, the dead-band dew point value DTD is pre-selected asa constant. In an alternative embodiment, the dead-band dew point valueDTD is defined as a function of ambient conditions, and morespecifically ambient static pressure PS or ambient dew point temperatureTD. Additionally, in one embodiment, the dead-band dew point value DTDis pre-selected to provide a dead-band of 3.0° F.

If the processor 36 determines that the determined static temperature TSis less than the combination of the measured dew point temperature TDand the dead-band dew point value DTD, the processor 36 maintains theoperating status of the ice protection system and re-starts the methodbeginning with measuring the static pressure PS, the total pressure PT,the total temperature TT, and the dew point temperature TD of theambient air. In one embodiment, when the processor 36 maintains theoperating status of the ice protection system, the processor 36 sends anadvisory signal to notify the aircraft flight crew the operating statusof the ice protection system is being maintained.

If the processor 36 determines that the determined static temperature TSis less than the measured dew point temperature TD, the processor 36concludes the ambient conditions, including the ambient air humidity,are conducive to ice formation. The processor 36 then sends an outputsignal to the ice protection system controller 26 that activates the iceprotection system. In one embodiment, when ambient conditions areconducive to ice formation, the processor 36 sends an advisory signal tonotify the aircraft flight crew the ambient conditions are conducive toice formation. Additionally, in one embodiment, when the processor 36has activated the ice protection system, the processor 36 sends anadvisory signal to notify the aircraft flight crew the ice protectionsystem has been activated. The method then re-starts, beginning withmeasuring the static pressure PS, the total pressure PT, the totaltemperature TT, and the dew point temperature TD of the ambient air, tore-evaluate ambient air conditions.

FIG. 8 is a flow chart illustrating an alternative exemplary method ofdetecting conditions conducive to ice formation on the aircraft surface32 (FIG. 1) using the icing conditions detection system 24 (FIGS. 1 and2), wherein ambient air moisture conditions are determined using aliquid water content sensor 42 (FIGS. 1 and 2). The method includesmeasuring the static pressure PS of ambient air adjacent the aircraft 20using the pressure sensor 38, measuring the total pressure PT of theambient air adjacent the aircraft 20 using the pressure sensor 38,measuring the total temperature TT of the ambient air adjacent theaircraft 20 using the temperature sensor 40, and measuring the liquidwater content LWC of the ambient air adjacent the aircraft 20 using theliquid water content sensor 42. The PS, PT, TT, and LWC measurements areinput into the processor 36 (FIGS. 1 and 2) from the respective sensors38, 40, 42.

The processor 36 determines the static temperature TS of the ambient airadjacent the aircraft 20. In one embodiment, the processor 36 calculatesthe static temperature TS using the measured static pressure PS, themeasured total pressure PT, and the measured total temperature TT. Theprocessor 36 uses the determined static temperature TS to determine ifthe ambient temperature conditions are conducive to ice formation. Morespecifically, the processor 36 compares the determined statictemperature TS with a minimum temperature for icing (T_(min)) and amaximum temperature for icing (T_(max)). As described below, if theprocessor 36 determines the determined static temperature TS is outsidethe defined temperature limits of T_(min) and T_(max), the processor 36concludes the ambient air static temperature TS is not conducive to iceformation and determines if the ice protection system, if operating,should be de-activated. FIG. 7 is a graph illustrating the FAR Part 25Appendix C icing temperature and pressure boundaries for both continuousmaximum and intermittent maximum atmospheric icing conditions in termsof temperature versus ambient static pressure PS. FIG. 7 alsoillustrates the ambient static temperature TS (envelope ABCD) used bythe processor 36.

In the exemplary embodiments, the T_(min) and T_(max) are pre-selectedas constants, wherein T_(min) is selected as 40° F. and T_(max) isselected as +50° F. It should be understood that constant values for theT_(min) and T_(max) other than those exemplified herein may be used. Inan alternative embodiment, the T_(min) and T_(max) are defined as afunction of ambient static pressure PS. In one alternative embodiment,the processor 36 determines the T_(min) and the T_(max) for the measuredstatic pressure using a table, similar to FIG. 7, stored in theprocessor 36, or alternatively a memory (not shown) operativelyconnected to the processor 36, and plots the T_(min) and T_(max) versusambient static pressure PS. In another alternative embodiment, theprocessor 36 determines the T_(min) and T_(max) for the measured staticpressure PS using a mathematical relationship stored in the processor36, or alternatively a memory (not shown) operatively connected to theprocessor 36, that calculates the T_(min) and T_(max) as a function ofambient static pressure PS.

As discussed above, the processor 36 compares the determined statictemperature TS with the T_(min). If the processor determines thedetermined static temperature TS is less than the T_(min), the processor36 concludes the ambient air static temperature, and more specificallythe determined static temperature TS, is not conducive to ice formation,and determines if the ice protection system (not shown), if operating,should be de-activated. In one embodiment, when the processor 36concludes the ambient air static temperature is not conducive to iceformation, the processor 36 sends an advisory signal to notify theaircraft flight crew the ambient air temperature is not conducive to iceformation. To determine if the ice protection system should bedeactivated, the processor 36 compares the determined static temperatureTS to the difference between the T_(min) and a dead-band minimumtemperature value (δT_(min)). The δT_(min) provides increased safety andprevents cyclic activation and de-activation of the ice protectionsystem when the ambient air temperature, and more specifically thedetermined static temperature TS, is marginally conducive to iceformation. If the processor 36 determines that the determined statictemperature TS is less than the difference between the T_(min) and theδT_(min), the processor 36 sends an output signal to the ice protectionsystem controller 26 to de-activate the ice protection system if it isoperating, and the processor re-starts the method beginning withmeasuring the static pressure PS, the total pressure PT, the totaltemperature TT, and the dew point temperature TD of the ambient air. Inone embodiment, when the ice protection system has been de-activated,the processor 36 sends an advisory signal to notify the aircraft flightcrew the ice protection system has been de-activated.

If the processor 36 determines the determined static temperature TS isgreater than or equal to the difference between the T_(min) and theδT_(min), the processor 36 maintains the operating status of the iceprotection system and re-starts the method beginning with measuring thestatic pressure PS, the total pressure PT, the total temperature TT, andthe dew point temperature TD of the ambient air. In one embodiment, whenthe processor 36 maintains the operating status of the ice protectionsystem, the processor 36 sends an advisory signal to notify the aircraftflight crew that the operating status of the ice protection system isbeing maintained.

If the processor 36 determines the determined static temperature TS isgreater than or equal to the T_(min), the processor 36 concludes theambient air static temperature, and more specifically the determinedstatic temperature TS, is conducive to ice formation. In one embodiment,when the processor 36 concludes the ambient air temperature is conduciveto ice formation, the processor 36 sends an advisory signal to notifythe aircraft flight crew that the ambient air temperature is conduciveto ice formation.

As discussed above, the processor 36 then compares the determined statictemperature TS with the T_(max). If the processor determines thedetermined static temperature TS is greater than or equal to theT_(max), the processor 36 concludes the ambient air static temperature,and more specifically the determined static temperature TS, is notconducive to ice formation, and determines if the ice protection system,if operating, should be de-activated. In one embodiment, when theprocessor 36 concludes the ambient air static temperature is notconducive to ice formation, the processor 36 sends an advisory signal tonotify the aircraft flight crew the ambient air temperature is notconducive to ice formation. To determine if the ice protection systemshould be de-activated, the processor 36 compares the determined statictemperature TS to the combination of the T_(max) and a dead-band maximumtemperature value (δT_(max)). The δT_(max) provides increased safety andprevents cyclic activation and de-activation of the ice protectionsystem when the ambient air temperature, and more specifically thedetermined static temperature TS, is marginally conducive to iceformation. If the processor 36 determines that the determined statictemperature TS is greater than or equal to the combination of theT_(max) and the δT_(max), the processor 36 sends an output signal to theice protection system controller 26 to de-activate the ice protectionsystem if it is operating, and the processor re-starts the methodbeginning with measuring the static pressure PS, the total pressure PT,the total temperature TT, and the dew point temperature TD of theambient air. In one embodiment, when the ice protection system has beende-activated, the processor 36 sends an advisory signal to notify theaircraft flight crew the ice protection system has been de-activated.

If the processor 36 determines the determined static temperature TS isless than the combination of the T_(max) and the δT_(max), the processor36 maintains the operating status of the ice protection system andre-starts the method beginning with measuring the static pressure PS,the total pressure PT, the total temperature TT, and the dew pointtemperature TD of the ambient air. In one embodiment, when the processor36 maintains the operating status of the ice protection system, theprocessor 36 sends an advisory signal to notify the aircraft flight crewthat the operating status of the ice protection system is beingmaintained.

If the processor 36 determines the determined static temperature TS isless than the T_(max), the processor 36 concludes the ambient air statictemperature, and more specifically the determined static temperature TS,is conducive to ice formation. In one embodiment, when the processor 36concludes the ambient air temperature is conducive to ice formation, theprocessor 36 sends an advisory signal to notify the aircraft flight crewthat the ambient air temperature is conducive to ice formation.

In the exemplary embodiments, the dead-band temperature values δT_(min)and δT_(max) are pre-selected as constants, wherein the δT_(min) isselected as 2° F. and the δT_(max) is selected as 5° F. It should beunderstood that constant values for the δT_(min) and the δT_(max) otherthan those exemplified herein may be used. In an alternative embodiment,the dead-band temperature values δT_(min) and δT_(max) are defined as afunction of ambient conditions, and more specifically ambient staticpressure PS.

The processor 36 then determines whether the ambient humidity conditionsare conducive to ice formation. More specifically, the processor 36compares the measured liquid water content LWC with a threshold liquidwater content for icing (THLWC). In the exemplary embodiment, thethreshold liquid water content for icing (THLWC) is pre-selected as aconstant, wherein the threshold liquid water content for icing THLWC isselected as 0.02 grams/cubic meter. It should be understood thatconstant values for the threshold liquid water content for icing THLWCother than the value exemplified herein may be used. In an alternativeembodiment, the threshold liquid water content for icing THLWC isdefined as a function of ambient static pressure PS. In one alternativeembodiment, the processor 36 determines the threshold liquid watercontent for icing THLWC for the measured static pressure PS using atable, similar to FIG. 7, stored in the processor 36, or alternatively amemory (not shown) operatively connected to the processor 36, and plotsthe threshold liquid water content for icing THLWC versus ambient staticpressure PS. In another alternative embodiment, the processor 36determines the threshold liquid water content for icing THLWC for themeasured static pressure PS using a mathematical relationship stored inthe processor 36, or alternatively a memory (not shown) operativelyconnected to the processor 36, that calculates the threshold liquidwater content for icing THLWC as a function of ambient static pressurePS.

If the processor 36 determines the measured liquid water content LWC isless the threshold liquid water content for icing THLWC, the processor36 concludes the ambient air humidity is not conducive to ice formation,and determines if the ice protection system, if operating, should bede-activated. In one embodiment, when the processor 36 concludes theambient air humidity is not conducive to ice formation, the processor 36sends an advisory signal to notify the aircraft flight crew that theambient air humidity is not conducive to ice formation. To determine ifthe ice protection system should be deactivated, the processor 36compares the measured liquid water content LWC to the difference betweenthe threshold liquid water content for icing THLWC and a dead-bandthreshold liquid water content for icing (δTHLWC). The dead-bandthreshold liquid water content for icing δTHLWC provides additionalsafety and prevents cyclic activation and de-activation of the iceprotection system when the ambient air humidity is marginally conduciveto ice formation.

In the exemplary embodiment, the dead-band threshold liquid watercontent for icing δTHLWC is pre-selected as a constant, wherein theδTHLWC is selected as 0.002 grams/cubic meter. It should be understoodthat constant values for the δTHLWC other than the value exemplifiedherein may be used. In an alternative embodiment, the dead-bandthreshold liquid water content for icing δTHLWC is defined as a functionof ambient conditions, and more specifically ambient static pressure PS.

If the processor 36 determines the measured liquid water content LWC isless than the difference between the threshold liquid water content foricing THLWC and the dead-band threshold liquid water content for icing(δTHLWC), the processor 36 sends an output signal to the ice protectionsystem controller 26 to de-activate the ice protection system if it isoperating, and the processor 36 re-starts the method beginning withmeasuring the static pressure PS, the total pressure PT, the totaltemperature TT, and the liquid water content LWC of the ambient air. Inone embodiment, when the ice protection system has been de-activated,the processor 36 sends an advisory signal to notify the aircraft flightcrew the ice protection system has been de-activated.

If the processor 36 determines the measured liquid water content LWC isgreater than or equal to the difference between the threshold liquidwater content for icing THLWC and the dead-band threshold liquid watercontent for icing (δTHLWC), the processor 36 maintains the operatingstatus of the ice protection system and re-starts the method beginningwith measuring the static pressure PS, the total pressure PT, the totaltemperature TT, and the liquid water content LWC of the ambient air. Inone embodiment, when the processor 36 maintains the operating status ofthe ice protection system, the processor 36 sends an advisory signal tonotify the aircraft flight crew the operating status of the iceprotection system is being maintained.

If the processor 36 determines the measured liquid water content LWC isgreater than or equal to the threshold liquid water content for icingTHLWC, the processor 36 concludes the ambient conditions, including theambient air humidity, are conducive to ice formation. The processor 36then sends an output signal to the ice protection system controller 26that activates the ice protection system. In one embodiment, whenambient conditions are conducive to ice formation, the processor 36sends an advisory signal to notify the aircraft flight crew the ambientconditions are conducive to ice formation. Additionally, in oneembodiment, when the processor 36 has activated the ice protectionsystem, the processor 36 sends an advisory signal to notify the aircraftflight crew the ice protection system has been activated. The methodthen re-starts, beginning with measuring the static pressure PS, thetotal pressure PT, the total temperature TT, and the liquid watercontent LWC of the ambient air, to re-evaluate ambient air conditions.

Although the methods are described and illustrated herein in theexemplary manner, it should be understood that the methods might includethe measurement and use of other parameters that may or may not bedescribed herein to detect conditions conducive to ice formation. Forexample, although the exemplary methods described herein use either adew point temperature sensor or a liquid water content sensor to detectambient moisture conditions, it should be understood that the methodsdescribed herein may use other sensor types that may or may not bedescribed herein to detect ambient moisture conditions. Additionally,although the methods are described and illustrated herein as includingthe measurement and use of a static pressure, a total pressure, a totaltemperature, and either a dew point temperature or a liquid watercontent, it should be understood that the method may not include themeasurement and use of all of such parameters (static pressure, totalpressure, total temperature, dew point temperature, and/or liquid watercontent), but rather, the method may include the measurement and use ofany number of these parameters, alone or in combination, to detectconditions conducive to ice formation.

The above-described detection system is cost-effective and reliable fordetecting conditions conducive to ice formation. More specifically, inthe exemplary embodiment, the detection system measures a staticpressure, a total pressure, a total temperature, and either a dew pointtemperature or a liquid water content, and processes the measurements todetermine whether conditions conducive to ice formation are present.Based on the determination of whether conditions conducive to iceformation are present, the detection system may automatically controlice protection systems, and may also generate advisory signals. In theexemplary embodiment, the detection system determines whether ambientair conditions are conducive to the formation of ice on the surfaces ofan aircraft. Based on whether ambient air conditions are conducive toice formation, the exemplary detection system automates ice protectionsystems for the aircraft engine and flight surfaces, and generatesadvisory signals for the aircraft flight crew. The exemplary detectionsystem is operable over the complete range of FAR icing environments.

Although the invention is herein described and illustrated inassociation with an aircraft, and more specifically, in association withthe detection of ambient conditions conducive to ice formation onsurfaces of the aircraft, it should be understood that the presentinvention is generally applicable to the detection of conditionsconducive to ice formation in any context and/or with regard to anyvehicle. Accordingly, practice of the present invention is not limitedto the detection of ambient conditions conducive to ice formation on thesurfaces of an aircraft, nor is practice of the present inventionlimited to aircraft generally.

Exemplary embodiments of icing condition detection systems are describedabove in detail. The systems are not limited to the specific embodimentsdescribed herein, but rather, components of each system may be utilizedindependently and separately from other components described herein.Each icing condition detection system component can also be used incombination with other icing condition detection system components.

When introducing elements of the present invention or the preferredembodiment(s) thereof, the articles “a”, “an”, “the” and “said” areintended to mean that there are one or more of the elements. The terms“comprising”, “including” and “having” are intended to be inclusive andmean that there may be additional elements other than the listedelements.

As various changes could be made in the above constructions withoutdeparting from the scope of the invention, it is intended that allmatter contained in the above description or shown in the accompanyingdrawings shall be interpreted as illustrative and not in a limitingsense.

1. A method in a processor device for identifying conditions conduciveto the formation of ice, comprising: comparing, by the processor device,a static temperature value, representative of a static temperatureexternal to an aircraft, to a first threshold temperature and a secondthreshold temperature higher than the first; comparing at least one of(a) a liquid water content value of air in an air collection passage,representative of a liquid water content external to the aircraft, to athreshold liquid water content, and (b) a dew point temperature of airin the air collection passage, representative of a dew point temperatureexternal to the aircraft, to a threshold dew point temperature; and ifthe static temperature value is at or above the first thresholdtemperature and at or below the second threshold temperature, and atleast one of (a) the liquid water content value is at or above thethreshold liquid water content, and (b) the dew point temperature isbelow the static temperature, directing an action associated withconditions conducive to ice formation.
 2. The method of claim 1 whereindirecting an action includes directing an advisory signal.
 3. The methodof claim 1 wherein directing an action includes directing activation ofan ice protection system.
 4. The method of claim 3 wherein directingactivation of an ice protection system includes directing activation ofan ice protection system positioned at a wing leading edge of theaircraft.
 5. The method of claim 3 wherein directing activation of anice protection system includes directing activation of an ice protectionsystem positioned at an inlet of the aircraft.
 6. The method of claim 1,further comprising carrying out the following operations if the statictemperature value is below the first threshold temperature: comparingthe static temperature value to the difference between the firstthreshold temperature and a deadband temperature value; if the statictemperature value is greater than or equal to the difference,maintaining an ice protection system aboard the aircraft in an activestate; and if the static temperature value is less than the differenceand the ice protection system is in an active state, deactivating theice protection system.
 7. The method of claim 1, further comprisingcarrying out the following operations if the static temperature value isabove the second threshold temperature: comparing the static temperaturevalue to the sum of the second threshold temperature and a deadbandtemperature value; if the static temperature value is less than the sum,maintaining an ice protection system aboard the aircraft in an activestate; and if the static temperature value is greater than or equal tothe sum, and the ice protection system is in an active state,deactivating the ice protection system.
 8. The method of claim 1,further comprising carrying out the following operations if the liquidwater content value is above the threshold liquid water content:comparing the liquid water content value to the sum of the thresholdliquid water content and a deadband liquid water content value; if theliquid water content value is greater than or equal to the sum,maintaining an ice protection system aboard the aircraft in an activestate; and if the liquid water content value is less than the sum, andthe ice protection system is in an active state, deactivating the iceprotection system.
 9. The method of claim 1, further comprising:receiving an indication of a static pressure and a total pressureexternal to the aircraft; receiving an indication of a total temperatureand a liquid water content external to an aircraft; and determining thestatic temperature value based at least in part on a measured totaltemperature.
 10. The method of claim 9, further comprising determiningat least one of the first and second threshold temperatures as afunction of the static pressure.
 11. The method of claim 9, furthercomprising determining the second threshold temperature as a function ofthe static pressure.
 12. The method of claim 9, wherein determining thestatic temperature value includes determining the static temperaturevalue based at least in part on the total temperature, the staticpressure, and the total pressure.
 13. The method of claim 1 whereincomparing the static temperature value includes comparing the statictemperature value to a first threshold temperature having a constantvalue.
 14. The method of claim 1 wherein comparing the statictemperature value includes comparing the static temperature value to asecond threshold temperature having a constant value.
 15. The method ofclaim 1 wherein comparing the static temperature value includescomparing the static temperature value to a first threshold temperaturethat is a function of the static pressure.
 16. The method of claim 1,further comprising determining at least one of the first and secondthreshold temperatures from a table.
 17. The method of claim 1, furthercomprising determining at least one of the first and second thresholdtemperatures from a mathematical relation.